FR3111662B1 - Dispositif d’etancheite entre un distributeur de turbine haute pression et une chambre de combustion - Google Patents

Dispositif d’etancheite entre un distributeur de turbine haute pression et une chambre de combustion Download PDF

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Publication number
FR3111662B1
FR3111662B1 FR2006315A FR2006315A FR3111662B1 FR 3111662 B1 FR3111662 B1 FR 3111662B1 FR 2006315 A FR2006315 A FR 2006315A FR 2006315 A FR2006315 A FR 2006315A FR 3111662 B1 FR3111662 B1 FR 3111662B1
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FR
France
Prior art keywords
sealing device
high pressure
combustion chamber
pressure turbine
distributor
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
FR2006315A
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English (en)
Other versions
FR3111662A1 (fr
Inventor
Dan-Ranjiv Joory
Jacques Marcel Arthur Bunel
Benjamin Frantz Karl Villenave
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
Safran Aircraft Engines SAS
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Safran Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
Priority to FR2006315A priority Critical patent/FR3111662B1/fr
Publication of FR3111662A1 publication Critical patent/FR3111662A1/fr
Application granted granted Critical
Publication of FR3111662B1 publication Critical patent/FR3111662B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16J—PISTONS; CYLINDERS; SEALINGS
    • F16J15/00—Sealings
    • F16J15/02—Sealings between relatively-stationary surfaces
    • F16J15/06—Sealings between relatively-stationary surfaces with solid packing compressed between sealing surfaces
    • F16J15/08—Sealings between relatively-stationary surfaces with solid packing compressed between sealing surfaces with exclusively metal packing
    • F16J15/0887—Sealings between relatively-stationary surfaces with solid packing compressed between sealing surfaces with exclusively metal packing the sealing effect being obtained by elastic deformation of the packing
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Gasket Seals (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

DISPOSITIF D’ETANCHEITE ENTRE UN DISTRIBUTEUR DE TURBINE HAUTE PRESSION ET UNE CHAMBRE DE COMBUSTION Un aspect de l’invention concerne un dispositif d’étanchéité (1) entre une chambre de combustion et un distributeur haute pression, ledit dispositif d’étanchéité (1) comportant : un secteur de disque (2) construit et agencé pour être fixé sur une paroi radiale d’un anneau de distributeur ;un secteur d’anneau de maintien (3), ledit secteur d’anneau de maintien (3) comportant une première extrémité (4) disposée à la périphérie externe (5) dudit secteur de disque (2) ;un élément souple (6) disposé sur une deuxième extrémité (7) dudit secteur d’anneau de maintien (3). Figure à publier avec l’abrégé : Figure 2
FR2006315A 2020-06-17 2020-06-17 Dispositif d’etancheite entre un distributeur de turbine haute pression et une chambre de combustion Active FR3111662B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR2006315A FR3111662B1 (fr) 2020-06-17 2020-06-17 Dispositif d’etancheite entre un distributeur de turbine haute pression et une chambre de combustion

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2006315 2020-06-17
FR2006315A FR3111662B1 (fr) 2020-06-17 2020-06-17 Dispositif d’etancheite entre un distributeur de turbine haute pression et une chambre de combustion

Publications (2)

Publication Number Publication Date
FR3111662A1 FR3111662A1 (fr) 2021-12-24
FR3111662B1 true FR3111662B1 (fr) 2022-12-23

Family

ID=72709509

Family Applications (1)

Application Number Title Priority Date Filing Date
FR2006315A Active FR3111662B1 (fr) 2020-06-17 2020-06-17 Dispositif d’etancheite entre un distributeur de turbine haute pression et une chambre de combustion

Country Status (1)

Country Link
FR (1) FR3111662B1 (fr)

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB9305010D0 (en) * 1993-03-11 1993-04-28 Rolls Royce Plc A cooled turbine nozzle assembly and a method of calculating the diameters of cooling holes for use in such an assembly
US6547257B2 (en) * 2001-05-04 2003-04-15 General Electric Company Combination transition piece floating cloth seal and stage 1 turbine nozzle flexible sealing element
FR2829796B1 (fr) 2001-09-20 2003-12-12 Snecma Moteurs Dispositif de maintien des joints de plates-formes de secteurs de distributeur de turbomachine a lamelles d'etancheite
US7246995B2 (en) * 2004-12-10 2007-07-24 Siemens Power Generation, Inc. Seal usable between a transition and a turbine vane assembly in a turbine engine
FR2887588B1 (fr) * 2005-06-24 2011-06-03 Snecma Moteurs Interface ventilee entre une chambre de combustion et un distributeur haute pression de turboreacteur et turboreacteur comportant cette interface
US10344609B2 (en) * 2014-10-24 2019-07-09 United Technologies Corporation Bifurcated sliding seal

Also Published As

Publication number Publication date
FR3111662A1 (fr) 2021-12-24

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